Gas turbine engine oil tank

ABSTRACT

A gas turbine engine includes an engine static structure housing that includes a compressor section and a turbine section. A combustor section is arranged axially between the compressor section and the turbine section. A core nacelle encloses the engine static structure to provide a core compartment. An oil tank is arranged in the core compartment and is axially aligned with the compressor section. A heat exchanger is secured to the oil tank and arranged in the core compartment.

CROSS-REFERENCE TO RELATED APPLICATIONS

This application is a continuation of U.S. application Ser. No.14/806,809, filed Jul. 23, 2015, which is a continuation of U.S.application Ser. No. 13/465,637, filed May 7, 2012, now U.S. Pat. No.9,194,294 granted Nov. 24, 2015, both of which are incorporated hereinby reference.

BACKGROUND

This disclosure relates to an oil tank for a gas turbine engine.

Lubrication systems for gas turbine engines require significant amountsof lubrication oil, which must be provided to numerous internal andexternal components during operation. Typically, an oil pump is mountedon an accessory gearbox, which may be located at various locationsrelative to the gas turbine engine, for example, within core and/or fannacelles.

Oil tanks are typically located in the vicinity of the accessorygearbox, with fluid lines running to the gearbox, oil pump, engine sumpand oil coolers, for example. Due to packaging constraints, the oil tankmay be located near the hot section of the gas turbine engine, forexample, in the vicinity of the combustor section and the turbinesection. Alternatively, the oil tank may be packaged in a fan nacelledue to spatial constraints about the core.

SUMMARY

In one exemplary embodiment, a gas turbine engine includes an enginestatic structure housing that includes a compressor section and aturbine section. A combustor section is arranged axially between thecompressor section and the turbine section. A core nacelle encloses theengine static structure to provide a core compartment. An oil tank isarranged in the core compartment and is axially aligned with thecompressor section. A heat exchanger is secured to the oil tank andarranged in the core compartment.

In a further embodiment of any of the above, the compressor sectionincludes a low pressure compressor section that is arranged axiallyupstream from a high pressure compressor section. The oil tank isaxially aligned with at least a portion of the low pressure compressorsection.

In a further embodiment of any of the above, the compressor and turbinesections are mounted on at least one spool, and the engine includes afan case that houses a fan connected to the spool. A fan nacelleencloses the fan case, and a bypass flow path is provided between thecore and fan nacelles.

In a further embodiment of any of the above, the gas turbine engineincludes a radial structure that interconnects the engine staticstructure and the fan case. A lubrication passage extends through theradial structure, and a tube fluidly interconnects the lubricationpassage to the oil tank.

In a further embodiment of any of the above, the radial structureincludes flow exit guide vanes.

In a further embodiment of any of the above, the flow exit guide vaneincludes a radially extending cavity that provides the lubricationpassage.

In a further embodiment of any of the above, the flow exit guide vaneincludes a radially extending cavity. A conduit is arranged in thecavity and fluidly connects to the tube.

In a further embodiment of any of the above, the gas turbine engineincludes a fill tube mounted to the fan case. The fan nacelle includes acover configured to be removably secured over the fill tube.

In a further embodiment of any of the above, the fan nacelle includes acover configured to be removably secured over the fill tube.

In a further embodiment of any of the above, the gas turbine engineincludes at least one bearing compartment that is configured to supportthe spool, and a lubrication system having a gearbox that is arranged inthe core compartment and includes a lubrication pump. The lubricationpump us fluidly connected to the oil tank and the bearing compartment.

In a further embodiment of any of the above, the gas turbine engineincludes a heat exchanger that is secured to the oil tank.

In a further embodiment of any of the above, the oil tank includes aportion that extends through an opening in the core nacelle and isexposed to the bypass flow path.

In a further embodiment of any of the above, the oil tank includes anexterior surface that is arranged in the opening. The core nacelle hasan outer contour facing the bypass flow path, and the exterior surfacefollowing the outer contour.

In a further embodiment of any of the above, the oil tank is arcuate inshape and is arranged axially forward of a gearbox mounted to the enginestatic structure.

In a further embodiment of any of the above, the oil tank includes awall having fins that extend through slots providing the opening andinto the bypass flow path.

In another exemplary embodiment, A gas turbine engine includes an enginestatic structure that is supported relative to a fan case by a radialstructure. An oil tank is mounted to the engine static structure. An oilfill tube is mounted to the fan case and is fluidly connected to the oiltank. A fan nacelle enclosing the fan case and including a removablecover arranged over the oil fill tube.

In a further embodiment of any of the above, the gas turbine engineincludes a core nacelle enclosing the engine static structure to providea core compartment. The oil tank is arranged in the core compartment.

In a further embodiment of any of the above, the gas turbine engineincludes a lubrication passage that is arranged in the radial structurefluidly interconnecting the oil fill tube to the oil tank.

In another exemplary embodiment, a gas turbine engine includes an enginestatic structure that is supported relative to a fan case by a radialstructure. A lubrication passage extends through the radial structure.The engine static structure houses a compressor section and a turbinesection. A combustor section is arranged axially between the compressorsection and the turbine section. A core nacelle encloses the enginestatic structure to provide a core compartment. An oil tank is arrangedin the core compartment and axially aligned with the compressor section.A heat exchanger is secured to the oil tank and arranged in the corecompartment. An oil fill tube is mounted to the fan case and fluidlyinterconnects the lubrication passage to the oil tank. A fan nacelleencloses the fan case and includes a removable cover arranged over theoil fill tube.

BRIEF DESCRIPTION OF THE DRAWINGS

The disclosure can be further understood by reference to the followingdetailed description when considered in connection with the accompanyingdrawings wherein:

FIG. 1 is a schematic side perspective view of an example gas turbineengine.

FIG. 2 is another perspective view of the gas turbine engine shown inFIG. 1.

FIG. 3 is a top elevational view of the gas turbine engine in the areaof a fan case.

FIG. 4 is a perspective view of an example accessory gearbox.

FIG. 5A is a schematic cross-sectional view of a fan case and staticstructure with a radial structure having example lubrication passage.

FIG. 5B is a schematic cross-sectional view of another example fan case,radial structure and lubrication passage.

FIG. 6A is an end view of an example oil tank.

FIG. 6B is an end view of another example oil tank.

FIG. 7 is a schematic depiction of a heat exchanger mounted to theexample oil cooler.

FIG. 8 is a schematic view of an example lubrication system.

DETAILED DESCRIPTION

An exemplary gas turbine engine 10 is schematically depicted in FIG. 1.The engine 10 may be a high bypass engine, as shown, or any otherdesired configuration. It should be understood that the disclosedfeatures, such as the oil tank, oil fill and core nacelle describedbelow may relate to other types of engines.

The engine 10 includes a fan case 12 supported relative to an enginestatic structure 16 by radial structure 14, such as flow exit guidevanes. Alternatively, struts may provide the radial structure 14. Theengine 10 is supported relative to an airframe by a pylon 18.

A fan 20 is housed within the fan case 12, and a fan nacelle 24surrounds the fan case 12. A core nacelle 22 surrounds the engine staticstructure 16 and provides a bypass flowpath 26 together with the fannacelle 24.

The positions of a low pressure compressor section 28, high pressurecompressor section 30, combustor section 32, high pressure turbinesection 34, and low pressure turbine section 36 within the engine staticstructure 16 are schematically depicted. The example engine 10 includesa dual spool arrangement in which the low pressure compressor section 28and low pressure turbine section 36 are mounted on an inner spool, andthe high pressure compressor section 30 and high pressure turbinesection 34 are mounted on an outer spool. A spool 37 is schematicallydepicted in FIG. 1 and may be an inner spool, for example, coupled tothe fan 20 directly or by a geared architecture.

An accessory gearbox 38, which may be V-shaped for packaging, is mountedon the engine static structure 16. Referring to FIG. 4, the gearbox 38includes an input shaft 40 coupled to at least one spool within theengine 10 to provide rotational drive to accessory drive components42A-42E mounted on the gearbox 38. The accessory drive components42A-42E may include an oil pump, a fuel pump, a hydraulic pump, astarter and a generator, for example. In the example, the gearbox 38 isgenerally axially aligned with the compressor section of the engine 10.

A core compartment 46 is provided between the core nacelle 22 and theengine static structure 16. The gearbox 38 is arranged within the corecompartment 46. An oil sump or oil tank 44 is also housed within thecore compartment 46 in a position axially forward of the gearbox 38, asbest shown in FIG. 1. In the example shown, the oil tank 44 is axiallyaligned with the compressor section, and in one example, axially alignedand outboard of the low pressure compressor section 28.

Referring to FIGS. 1 and 2, the fan case 12 provides an outer structure48. An inner structure 50 may be provided by the engine static structure16, for example. The flow exit guide vanes 14 extend between andinterconnect the outer and inner structure 48, 50. Referring to FIGS. 2and 3, a fill tube 52 may be mounted on the outer structure 48 toprovide oil to the oil tank 44. A cap 54 may be secured over the filltube 52 to provide a seal. A tube 62 carries the oil from the oil filltube 52 to the oil tank 44, as best illustrated in FIG. 2.

Referring to FIG. 5A, the fan nacelle 24 includes a cover 56 that isremovably secured over the oil fill tube 52, thus providing access tothe oil tank 44 for providing additional oil at service intervals. Inthe example illustrated in FIG. 5A, a fluid conduit 60 extends to acavity 58 in the flow exit guide vane 14 to fluidly connect the filltube 52 to the tube 62. In an example illustrated in FIG. 5B, the fancase 112 provides the outer structure 148. The cavity 158 is “wet” suchthat oil from the fill tube 152 flows through the flow exit guide vane114 and contacts the surfaces of the cavity 158, thus eliminating theneed for additional tubing.

The oil tank 44 is configured in an arcuate shape for packaging withinthe core compartment 46 between the core nacelle 22 and the enginestatic structure 16. The core nacelle 22 provides an outer contour 63that is circular in shape. The core nacelle 22 includes an opening 66,which exposes an exterior surface 64 of an outer wall 65 of the oil tank44. Oil within the cavity 67 of the oil tank 44 convectively transfersheat to the bypass flowpath 26 with the exterior surface 64 exposed.

Referring to FIG. 6B, the oil tank 144 includes fins 68 that extendthrough slots provided by the opening 166. The core nacelle 122 coversmuch of the oil tank 44 for protection from debris while permittingportions, such as the fins 68, to extend into the bypass flowpath 26 forimproved heat transfer.

Referring to FIG. 7, a heat exchanger 70 may be mounted to the oil tank44 using a fastening arrangement 72. Alternatively, the heat exchanger70 may be integrally formed and share a common wall with the oil tank44. The heat exchanger 70 may be exposed to airflow in some suitablefashion.

An example lubrication system 74 is schematically illustrated in FIG. 8.The lubrication system 74 includes a lubrication pump 76, which may bean accessory driven by the gearbox 38. The pump 76 may provide oil tothe heat exchanger 70 for cooling. The cooled oil is provided tomultiple components within the engine 10, for example, bearingcompartments 78A-78C. The bearings may support the spool 37. The oilfrom the bearing compartment 78A-78C is returned to the oil tank 44. Ade-aerator 80 may be fluidly connected to the oil tank 44 and may alsoinclude a vent 82 for venting air within the oil tank 44 to atmosphere.Oil may be added to the oil tank 44 by the fill tube 52, describedabove.

Although example embodiments have been disclosed, a worker of ordinaryskill in this art would recognize that certain modifications would comewithin the scope of the claims. For that reason, the following claimsshould be studied to determine their true scope and content.

What is claimed is:
 1. A gas turbine engine comprising: an engine staticstructure housing a compressor section and a turbine section, and acombustor section arranged axially between the compressor section andthe turbine section; a core nacelle enclosing the engine staticstructure to provide a core compartment; an oil tank arranged in thecore compartment and axially aligned with the compressor section; and alubrication pump configured to provide oil from the oil tank to the heatexchanger; wherein the core nacelle has an opening into the corecompartment, and the opening exposes an exterior surface of the oiltank.
 2. The gas turbine engine of claim 1, further comprising a heatexchanger secured to the oil tank and arranged in the core compartment.3. The gas turbine engine of claim 2, wherein the heat exchanger isintegrally formed and shares a common wall with the oil tank.
 4. The gasturbine engine of claim 2, wherein the heat exchanger is mounted to theoil tank using a fastening arrangement.
 5. The gas turbine engine ofclaim 2, wherein the lubrication pump is arranged fluidly between theoil tank and the heat exchanger.
 6. The gas turbine engine of claim 1,wherein the opening is multiple slots in the core nacelle.
 7. The gasturbine engine of claim 6, wherein the oil tank includes a wall havingfins extending through the slots.
 8. The gas turbine engine of claim 1,wherein a portion of the oil tank extends through the opening into thebypass flow path.
 9. The gas turbine engine of claim 8, wherein theportion of the oil tank includes fins.
 10. The gas turbine engine ofclaim 1, wherein the compressor and turbine sections are mounted on atleast one spool, and comprising a fan case housing a fan connected tothe at least one spool, a fan nacelle enclosing the fan case, and abypass flow path provided between the core and fan nacelles.
 11. The gasturbine engine of claim 10, further comprising a radial structureinterconnecting the engine static structure and the fan case, alubrication passage extending through the radial structure, and a tubefluidly interconnecting the lubrication passage to the oil tank.
 12. Thegas turbine engine of claim 11, wherein the radial structure includesflow exit guide vanes.
 13. The gas turbine engine of claim 12, whereinthe flow exit guide vanes include a radially extending cavity providingthe lubrication passage.
 14. The gas turbine engine of claim 13, whereineach of the flow exit guide vanes includes a radially extending cavity,and a conduit arranged in the cavity and fluidly connected to the tube.15. The gas turbine engine of claim 1, wherein the compressor sectionincludes a low pressure compressor section arranged axially upstreamfrom a high pressure compressor section, and the oil tank is axiallyaligned with at least a portion of the low pressure compressor section.16. A gas turbine engine comprising: an engine static structure housinga compressor section and a turbine section, and a combustor sectionarranged axially between the compressor section and the turbine section;a core nacelle enclosing the engine static structure to provide a corecompartment and having slots providing openings into the corecompartment; an oil tank arranged in the core compartment; wherein thecompressor and turbine sections are mounted on at least one spool, andcomprising a fan case housing a fan connected to the spool, a fannacelle enclosing the fan case, and a bypass flow path provided betweenthe core and fan nacelles; and wherein the oil tank includes a wallhaving fins extending through the slots in the core nacelle.
 17. The gasturbine engine of claim 16, wherein the fins extend into the bypass flowpath.
 18. The gas turbine engine of claim 16, wherein the oil tank isaxially arranged with the compressor section.
 19. The gas turbine engineof claim 18, wherein the compressor section includes a low pressurecompressor section arranged axially upstream from a high pressurecompressor section, and the oil tank is axially aligned with at least aportion of the low pressure compressor section.
 20. The gas turbineengine of claim 16, further comprising an oil fill tube mounted to thefan case and fluidly connected to the oil tank.